Return-Path: Sender: (Marvin Kaye) To: lml Date: Sat, 21 Sep 2002 19:11:26 -0400 Message-ID: X-Original-Return-Path: Received: from imo-r07.mx.aol.com ([152.163.225.103] verified) by logan.com (CommuniGate Pro SMTP 4.0b8) with ESMTP id 1740753 for lml@lancaironline.net; Sat, 21 Sep 2002 02:40:09 -0400 Received: from LancairJim@aol.com by imo-r07.mx.aol.com (mail_out_v34.10.) id q.123.16f39168 (18707) for ; Sat, 21 Sep 2002 02:39:37 -0400 (EDT) From: LancairJim@aol.com X-Original-Message-ID: <123.16f39168.2abd6e29@aol.com> X-Original-Date: Sat, 21 Sep 2002 02:39:37 EDT Subject: Re:Fuel Tank Check Valve LNC2 X-Original-To: lml@lancaironline.net MIME-Version: 1.0 Content-Type: text/plain; charset="US-ASCII" Content-Transfer-Encoding: 7bit X-Mailer: AOL 7.0 for Windows US sub 10637 There is something about this business of adding check valves in the fuel tank vent lines that I don't understand. Hopefully, someone on the LML can explain it. The primary purpose of the fuel tank vent is to allow air to flow into the tank as fuel is withdrawn. However, the vent also has the secondary, but no less important task, of equalizing pressure inside the tank with ambient conditions. For example, if the plane is refueled at an airport which is at sea level, the air pressure within the tank will be at equilibrium with the atmosphere at roughly 14.7 psia. If the plane then departs and climbs to say 10,000 ft, atmospheric pressure will have dropped to roughly 10.1 psia. If there is a check valve in the vent line, air inside the tank cannot flow out the vent during the climb to equalize the pressure. Under these conditions, the pressure inside the tank will still be 14.7 psia and the pilot will be performing an inadvertent pressure test on the plane's fuel tanks with a differential pressure of 4.6 psid (i.e., 14.7 psia inside the tank minus 10.1 psia outside). I have read of builders rupturing their tanks at substantially lower differential pressures than this during leak testing. At 20,000 ft the theoretical differential pressure is about 7.9 psid. Implicit in this analysis are several assumptions: 1) A significant quantity of fuel is not withdrawn from the tank during the climb. 2) The fuel cap doesn't leak or depart the plane. 3) The fuel tank doesn't leak. 4) The check valve doesn't leak. 5) Temperature effects are presumed to be negligible. Is there something wrong with this analysis? What am I missing? Does everyone who installs a check valve in their vent line just assume that the check valve or gas cap will leak a sufficient amount to prevent overpressurization of the tank? Seems like a gross rationalization to me. If you are wrong, you could lose a helluva lot more than a few pints of petrol. Until someone can explain to my satisfaction how overpressurization is not an issue, I think I will continue to build my LNC2 without check valves in the vent lines and put up with the occasional loss of fuel. Jim McKibbin PS - A float valve makes a lot more sense to me than a check valve from a functional standpoint but I haven't a clue where you might get a suitable one or how to install it.